Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 18377 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Hartzell Propeller 

Inc. model HC–E4A–3( )/E10950( ) 

propellers. These propellers are installed on, 

but not limited to, Raytheon Beechcraft 

1900D airplanes. 

(d) The parentheses appearing in the 

propeller model number indicates the 

presence or absence of an additional letter(s) 

that varies the basic propeller model. This 

AD still applies regardless of whether these 

letters are present or absent in the propeller 

model designation. 

Unsafe Condition 

(e) This AD results from reports of 

excessive propeller vibration and of damaged 

or broken propeller blade thrust bearings 

found during routine and investigative 

propeller disassembly. We are issuing this 

AD to prevent propeller blade separation, 

damage to the airplane, and possible loss of 

airplane control. 

Interim Action 

(f) These actions are interim actions and 

we may take further rulemaking actions in 

the future. 

Compliance 

(g) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Initial Inspection, Rework, and Replacement 

(h) For propellers with 4,000 or more 

operating hours time-since-overhaul (TSO, 

initially inspect and rework the propeller 

blade retention radius and replace the 

propeller thrust bearing for each blade, 

within 100 operating hours. 

(i) For propellers with 2,000 or more 

operating hours TSO, but fewer than 4,000 

operating hours TSO, inspect and rework the 

propeller blade retention radius and replace 

the propeller thrust bearing, for each blade, 

at the next propeller disassembly. 

(j) Use paragraphs 3.G.(1) through 3.G.(8) of 

the Accomplishment Instructions of Hartzell 

Propeller Inc. Service Bulletin No. HC–SB–

61–287, Revision 2, dated October 24, 2006, 

to do the actions in paragraphs (h) and (i) of 

this AD. 

(k) Although Hartzell Propeller Inc. SB No. 

HC–SB–61–287, Revision 2, dated October 

24, 2006, states in paragraph 3.G.(6) of the 

Accomplishment Instructions, to install new 

blade thrust bearings if required, this AD 

requires always installing new blade thrust 

bearings. 

Repetitive Inspection, Rework, and 

Replacement 

(l) Thereafter, after every 3,000 additional 

operating hours time-in-service, inspect and 

rework the propeller blade retention radius 

and replace the propeller blade thrust 

bearing, for each blade. 

(m) Use paragraphs 3.G.(1) through 3.G.(8) 

of the Accomplishment Instructions of 

Hartzell Propeller Inc. SB No. HC–SB–61–

287, Revision 2, dated October 24, 2006, to 

do these actions. 

(n) Although paragraph 3.G.(6) of the 

Accomplishment Instructions of Hartzell 

Propeller Inc. SB No. HC–SB–61–287, 

Revision 2, dated October 24, 2006, states to 

install new blade thrust bearings if required, 

this AD requires always installing new blade 

thrust bearings. 

Definition 

(o) For the purpose of this AD, next 

propeller disassembly is defined as any 

maintenance requiring separating of the 

propeller hub halves. 

Previous Credit 

(p) Previous credit is allowed for 

inspections, rework, and replacements that 

were done using the Original or Revision 1 

of Hartzell Propeller Inc. SB No. HC–SB–61–

287, before the effective date of this AD. 

Alternative Methods of Compliance 

(q) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(r) Contact Tim Smyth, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

2300 East Devon Avenue, Des Plaines, IL 

60018; e-mail: tim.smyth@faa.gov; telephone: 

(847) 294–7132; fax: (847) 294–7834, for 

more information about this AD. 

Material Incorporated by Reference 

(s) You must use the Hartzell Propeller Inc. 

service information specified in Table 1 of 

this AD to perform the checks required by 

this AD. The Director of the Federal Register 

approved the incorporation by reference of 

the documents listed in Table 1 of this AD 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Hartzell Propeller Inc. 

Technical Publications Department, One 

Propeller Place, Piqua, OH 45356; telephone 

(937) 778–4200; fax (937) 778–4391, for a 

copy of this service information. You may 

review copies at the FAA, New England 

Region, Office of the Regional Counsel, 12 

New England Executive Park, Burlington, 

MA; or at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

TABLE 1.—INCORPORATION BY REFERENCE

Hartzell Propeller Inc. Service Bulletin No. Page Revision Date 

HC–SB–61–287, Total Pages: 32 ............................... ALL .............................................................................. 2 October 24, 2006. 

Appendix to HC–SB–61–287, Total Pages: 2 ............ ALL .............................................................................. 2 October 24, 2006. 

Issued in Burlington, Massachusetts, on 

April 3, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–6586 Filed 4–11–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22898; Directorate 

Identifier 2005–NE–10–AD; Amendment 39–

15021; AD 2007–08–04] 

RIN 2120–AA64 

Airworthiness Directives; McCauley 

Propeller Systems Models 3A32C406/ 

82NDB–X and D3A32C409/82NDB–X 

Propellers 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

McCauley Propeller Systems models 

3A32C406/82NDB–X and D3A32C409/ 

82NDB–X propellers, installed on 

Teledyne Continental Motors (TCM) IO–

520, TSIO–520, or IO–550 reciprocating 

engines. These propellers are herein 

referred to as C406 and C409 propellers, 

respectively. This AD requires adding 

an operational revolutions per minute 

(RPM) restriction on the C406 and C409 

propellers, and installing an RPM 

restriction placard in the cockpit. This 

AD also adds a 10,000-hour total timein-service (TIS) life limit for these 

propellers. This AD also removes from 


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18378 Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 

service any propeller that has 10,000 

hours or more total TIS, or that has an 

unknown total TIS. Also, this AD 

requires initial and repetitive propeller 

blade inspections for damage, and repair 

if necessary. This AD results from 

testing by the manufacturer that 

identified stress conditions that affect 

the fatigue life and damage tolerance of 

C406 and C409 propellers, when 

installed on TCM IO–520, TSIO–520, or 

IO–550 reciprocating engines. We are 

issuing this AD to prevent blade or hub 

failure that could result in separation of 

a propeller blade and loss of control of 

the airplane. 

DATES: This AD becomes effective May 

17, 2007. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of May 17, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

McCauley Propeller Systems, P.O. Box 

7704, Wichita, KS 67277–7704; 

telephone (800) 621–7767. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Jeff 

D. Janusz, Aerospace Engineer, Wichita 

Aircraft Certification Office, Small 

Airplane Directorate, 1801 Airport 

Road, Room 100, Wichita, KS 67209, 

telephone: 316–946–4148, fax: 316–

946–4107. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to McCauley Propeller Systems 

C406 and C409 propellers, installed on 

TCM IO–520, TSIO–520, or IO–550 

reciprocating engines. We published the 

proposed AD in the Federal Register on 

Nov. 16, 2005 (70 FR 69472). That 

action proposed to require adding an 

operational RPM restriction on the C406 

and C409 propellers, and installing an 

RPM restriction placard in the cockpit. 

We coordinated the proposed placard 

placement with the responsible Aircraft 

Certification Offices within the Small 

Airplane Directorate, and all proposed 

installations include a manifold 

pressure gauge. That action also 

proposed to add a 10,000-hour total 

time-in-service (TIS) life limit for these 

propellers. That action also proposed to 

remove from service any propeller that 

has 10,000 hours or more total TIS, or 

that has an unknown total TIS. Finally, 

that action proposed to require initial 

and repetitive propeller blade 

inspections for damage, and repair if 

necessary. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

(800) 647–5227) is located on the plaza 

level of the Department of 

Transportation Nassif Building at the 

street address stated in ADDRESSES. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Financial Burden and Potential Unsafe 

Condition 

One commenter states that this AD 

will impose a financial burden on 

owners and operators of airplanes with 

this propeller installation because of the 

increased number of inspections and 

additional wear on the propeller system 

increasing the probability of the 

propeller system failing. The commenter 

also suggests that stamping a letter on 

the propeller model to designate a lifelimited propeller could create a 

potentially unsafe condition because the 

stamping can create stress risers and if 

improperly treated after stamping, could 

contribute to corrosion. The commenter 

also notes that the airplane model 

designations are incorrect and we 

omitted one model from the airplane 

model listing. Finally, the commenter 

asks why we did not immediately 

ground the fleet using this propeller 

because of the described severity of the 

unsafe condition. We partially agree 

with the comments. Each is addressed 

in turn. The increased inspections 

required by this AD are necessary to 

resolve the unsafe condition. Owner 

operators must maintain their aircraft in 

an airworthy condition, which includes 

paying for maintenance. We considered 

that cost and discussed it in the cost 

section below. We did not change the 

AD. 

This AD will not result in additional 

wear and tear on the propellers, or in 

increased failures. This AD resolves an 

unsafe condition. All actions required 

are either performed with the propeller 

installed, or coincident with the next 

overhaul or major disassembly. An 

experienced, appropriately rated 

mechanic can do the inspection and 

rework without removing the propeller. 

We did not change the AD. 

The manufacturer carefully 

considered where to stamp the life limit 

indication to minimize any stress riser. 

We have no indications that his choice 

was wrong. We did not change the AD. 

We agree that this AD should include 

additional models. We changed the AD 

to include the Beech 35–A33 and 35–

B33. The Beech 35–A33 and 35–B33 are 

now included in Applicability 

paragraph (c) Table (1). 

Grounding the fleet that has the 

suspect propellers installed is not 

required. The unsafe condition 

identified is due to material fatigue. The 

actions required by this AD adequately 

address the unsafe condition. We did 

not change the AD. 

Eliminate the Repetitive Inspections of 

This AD 

Another commenter states that the AD 

does not include a terminating action to 

eliminate the recurring inspections 

necessary to comply with it. Even if an 

operator replaces the existing propeller 

with a new propeller, the recurring 

inspections are necessary as long as the 

replacement propeller is one of same 

models identified in the airworthiness 

directive. Additionally, the commenter 

notes that aircraft performance is also a 

consideration. This AD will require 

operating the engine and propeller 

combination in a less than full engine 

power regime, which could compromise 

safety in particular situations associated 

with departures, arrivals and clearing 

obstacles. We partially agree. 

This AD imposes the RPM and life 

limit to correct an unsafe condition. The 

recurring inspections are required to 

enhance safety. The RPM restriction, 

imposed propeller life limit, and 

periodic propeller blade inspection/ 

rework provide a cost effective means to 

correct the unsafe condition without 

prematurely retiring the propeller. The 

RPM restriction does not affect the 

engine full power ratings. Takeoff, 

climb, and descent values remain 

unchanged. Therefore, this AD does not 

compromise safety during departures, 

arrivals, and in clearing obstacles. We 

did not change the AD. 

Recall Impacted Propellers 

Another commenter believes that the 

FAA should require a recall of all 

propeller models listed in the AD so the 

manufacturer will be responsible for the 

cost of repair and replacement. We do 

not agree. 

The FAA cannot dictate commercial 

business decisions related to AD 

actions. We identified the unsafe 

condition and are imposing appropriate 

corrective action. We did not change the 

AD. 


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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 18379 

Extend the Comment Period 

Two commenters asked that we 

extend the comment period for the 

proposed rule to give the general 

aviation community added time to 

review non-proprietary data used to 

substantiate the proposed action and to 

make additional comments. We agree, 

and extended the comment period to 

give the aviation community time to 

respond. The comments that we 

responded to above include any 

additional comments that came in. 

Correct Date of Service Bulletin 

The proposed rule referenced 

McCauley Propeller Systems Alert 

Service Bulletin (ASB) No. ASB248, 

dated January 17, 2005. The correct date 

is April 19, 2005. We changed the AD 

to indicate the correct date of the service 

bulletin. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

This AD will affect about 2,350 C406 

and C409 propellers installed on 

airplanes of U.S. registry. We estimate it 

will take three work-hours per propeller 

to perform the proposed inspections and 

repairs. We also estimate it will take 

about 0.5 work-hour to install the 

proposed cockpit placard, and about 

950 airplanes will require the placard. 

The average labor rate is $80 per workhour. A replacement propeller blade set 

will cost about $5,200. We estimate 500 

propellers in the fleet (or about 21 

percent) would require propeller blade 

set replacement. Based on these figures, 

we estimate the total cost of the AD to 

U.S. operators to be $3,202,000. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 14 CFR part 39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2007–08–04 McCauley Propeller Systems: 

Amendment 39–15021. Docket No. 

FAA–2005–22898; Directorate Identifier 

2005–NE–10–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 17, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to McCauley Propeller 

Systems models 3A32C406/82NDB–X and 

D3A32C409/82NDB–X propellers, herein 

referred to as C406 and C409 propellers, 

respectively. These propellers are installed 

on, but not limited to, the airplanes in the 

following Table 1: 

TABLE 1.—AIRPLANES THAT PROPELLERS ARE INSTALLED ON, BUT NOT LIMITED TO

Airplane models With engine model 

Beech: 

A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, 

P35, S35, V35, V35A, V35B, 35–33, 35–A33, 35–B33, 35–C33, 

35–C33A, E33, E33A, E33C, F33, F33A, F33C, 36, A36, A45, 

and D45.

Teledyne Continental Motors (TCM) IO–520 series and IO–550 series 

reciprocating engines. 

Beech: 

A36TC, B36TC, S35, V35A, V35B ................................................... TCM TSIO–520 series reciprocating engines. 

Navion: 

A (L–17B, C), B, D, E, F, G, and H .................................................. TCM IO–550 and TSIO–520 series reciprocating engines. 

Unsafe Condition 

(d) This AD results from testing by the 

manufacturer that identified stress conditions 

that affect the fatigue life and damage 

tolerance of C406 and C409 propellers, when 

installed on TCM IO–520, TSIO–520, or IO–

550 reciprocating engines. We are issuing 

this AD to prevent blade or hub failure that 

could result in separation of a propeller blade 

and loss of control of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 


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18380 Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 

Installation of Cockpit Placard for RPM 

Restriction 

(f) Within 10 hours time-in-service (TIS) 

after the effective date of this AD, install a 

placard on the instrument panel as close to 

the tachometer as possible, that states, in 1⁄8

inch-high or higher characters, ‘‘Continuous 

operation between 2,350–2,450 RPM at or 

above 24′′ manifold pressure is prohibited’’. 

The placard shall have red letters, on a 

white contrasting background with a red 

border. For example: 

Continuous operation 

between 2,350–2,450 RPM 

at or above 24′′ manifold 

pressure is prohibited 

Propellers With Unknown Total Hours TIS, 

or 10,000 or More Hours Total TIS on the 

Effective Date of This AD 

(g) For propellers that the total TIS is 

unknown, or that have 10,000 or more hours 

total TIS on the effective date of this AD, 

remove the propeller from service within 50 

hours TIS after the effective date of this AD. 

Propellers With Fewer Than 10,000 Hours 

Total TIS on the Effective Date of This AD 

(h) For propellers with fewer than 10,000 

total hours TIS on the effective date of this 

AD, do the following: 

(1) Perform an inspection of the propeller 

blades and repair if necessary, within 100 

hours after the effective date of this AD, 

using paragraphs 2.B. through 2.F. of 

Accomplishment Instructions of McCauley 

Propeller Systems Alert Service Bulletin 

(ASB) No. ASB248, dated April 19, 2005. 

(2) At the next propeller overhaul or next 

major propeller disassembly, life-limit-stamp 

the letter ‘‘L’’ on the propeller hub and 

blades, using paragraph 3 of 

Accomplishment Instructions of McCauley 

Propeller Systems ASB No. ASB248, dated 

April 19, 2005. 

(3) Thereafter, within every 100 hours TIS 

or at next annual inspection, whichever 

occurs first, inspect, and repair if necessary, 

the propeller blades using paragraphs 2.B. 

through 2.F. of Accomplishment Instructions 

of McCauley Propeller Systems ASB No. 

ASB248, dated April 19, 2005. 

(4) Remove the propeller from service upon 

reaching the life limit of 10,000 hours total 

TIS. 

Alternative Methods of Compliance 

(i) The Manager, Wichita Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(j) Contact Jeff D. Janusz, Aerospace 

Engineer, Wichita Aircraft Certification 

Office, Small Airplane Directorate, 1801 

Airport Road, Room 100, Wichita, KS 67209; 

telephone: 316–946–4148, fax: 316–946– 

4107, for more information about this AD. 

Material Incorporated by Reference 

(k) You must use McCauley Propeller 

Systems Alert Service Bulletin No. ASB248, 

dated April 19, 2005, to perform the actions 

required by this AD. The Director of the 

Federal Register approved the incorporation 

by reference of this service bulletin in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact McCauley Propeller Systems, 

P.O. Box 7704, Wichita, Kansas; telephone 

(800) 621–7767, for a copy of this service 

information. You may review copies at the 

FAA, New England Region, Office of the 

Regional Counsel, 12 New England Executive 

Park, Burlington, MA; or the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/federalregister/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

April 4, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–6831 Filed 4–11–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27709; Directorate 

Identifier 2007–CE–028–AD; Amendment 

39–15020; AD 2007–08–03] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 172R, 172S, 

182T, T182T, 206H, and T206H 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) to 

supersede AD 2006–17–04, which 

applies to certain Cessna Aircraft 

Company (Cessna) Models 172R, 172S, 

182T, T182T, 206H, and T206H 

airplanes. AD 2006–17–04 currently 

requires you to inspect the two end 

fittings on each of the flexible fuel hoses 

located in the engine compartment for 

the correct torque values, and, if any 

incorrect torque values are found during 

the inspection, tighten the hose end 

fittings to the correct torque values. This 

AD results from four reports of loose 

fuel lines connected to the fuel servo or 

fuel flow transducer. Two reports were 

of in-flight engine failure on a Model 

T182T airplane. A third report was of 

in-flight engine failure on a Model 206H 

airplane. A fourth report was of a Model 

172S airplane losing engine power on 

final approach. Consequently, this AD 

would require you to establish the 

correct torque values of the end fittings 

on fuel hoses for certain Cessna Models 

172R, 172S, 182T, T182T, 206H, and 

T206H airplanes. This AD clarifies that 

the torque values need to be physically 

established and visual inspection only 

is not sufficient. We are issuing this AD 

to detect and correct potential loss of 

fuel flow, which may result in partial or 

complete loss of engine power and/or 

uncontrolled engine compartment fire 

due to fuel leakage forward of the 

firewall. 

DATES: This AD becomes effective on 

May 2, 2007. 

On May 2, 2007 the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive any comments on 

this AD by June 11, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590– 

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

To get the service information 

identified in this AD, contact The 

Cessna Aircraft Company, Product 

Support, P.O. Box 7706, Wichita, 

Kansas 67277–7706; telephone: (316) 

517–5800; facsimile: (316) 942–9006. 

To view the comments to this AD, go 

to http://dms.dot.gov. The docket 

number is FAA–2007–27709; 

Directorate Identifier 2007–CE–028–AD. 

FOR FURTHER INFORMATION CONTACT: 

Trenton Shepherd, Aerospace Engineer, 

Wichita ACO, 1801 Airport Road, Room 

100, Wichita, Kansas 67209; telephone: 

(316) 946–4143; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

One report of loose fuel hose 

connections to the fuel injector servo on 

a Cessna Model 172S airplane caused us 

to issue AD 2006–17–04, Amendment 

39–14725 (71 FR 47711, August 18, 

2006). AD 2006–17–04 on certain 

Cessna Models 172R, 172S, 182T, 

T182T, 206H, and T206H airplanes, 

currently requires you to: 

• Inspect the two end fittings on each 

of the flexible fuel hoses located in the 


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